GB1330853A - Apparatus for controlling the acceleration of a gas turbine - Google Patents

Apparatus for controlling the acceleration of a gas turbine

Info

Publication number
GB1330853A
GB1330853A GB4950870A GB4950870A GB1330853A GB 1330853 A GB1330853 A GB 1330853A GB 4950870 A GB4950870 A GB 4950870A GB 4950870 A GB4950870 A GB 4950870A GB 1330853 A GB1330853 A GB 1330853A
Authority
GB
United Kingdom
Prior art keywords
acceleration
turbine
fuel
controller
signal
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB4950870A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB1330853A publication Critical patent/GB1330853A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F01D19/02—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine-casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
    • H02P23/00—Arrangements or methods for the control of AC motors characterised by a control method other than vector control
    • H02P23/16—Controlling the angular speed of one shaft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Power Engineering (AREA)
  • Control Of Velocity Or Acceleration (AREA)
  • Control Of Turbines (AREA)

Abstract

1330853 Automatic acceleration control GENERAL ELECTRIC CO 19 Oct 1970 [19 Nov 1969] 49508/70 Heading G3R The acceleration of a gas turbine is controlled during the starting period by a speed-responsive signal which is applied through a network comprising capacitor 103 and resistors 105,107, differentiating the signal to the base of transistor 111. The emitter circuit of the transistor comprises a potentiometer 117 which is connected through an operational amplifier 45 to a circuit for regulating the amount of fuel supplied to the turbine. Adjustment of the potentiometer 117 controls the gain of the system while resistor 107 provides means for adjustment of the point at which acceleration control commences, without interaction with other factors controlling the operation of the turbine. The system comprises main speed and temperature controllers as well as a main start-up controller which is associated with the acceleration controller. Each of the main controllers applies a signal through a diode to a minimum value gate which is connected through an amplifier to the fuel control circuit. The speed controller assumes control after the turbine has started, while the temperature controller prevents thermal shock by restricting the input of fuel. The gate allows that controller which has the least positive output signal to take over control of the turbine, Fig. 1, (not shown). Initially the turbine is turned mechanically and fuel is witheld until a predetermined speed is reached. At that point, a negative signal is applied to line 43 so that the output of amplifier 45 becomes more positive to increase the fuel input to a given level. As soon as a flame is detected, the fuel supply is reduced for a warm-up period, at the end of which the potential of the line 43 is gradually increased in a negative sense by a capacitorresistor network (57, 59), Fig. 2, (not shown. The acceleration controller provides a positivegoing feedback signal to keep the acceleration constant. At the end of the acceleration period the turbine receives maximum fuel supply for full speed operation, acceleration control being reintroduced during load-lost conditions, Fig. 2, (not shown).
GB4950870A 1969-11-19 1970-10-19 Apparatus for controlling the acceleration of a gas turbine Expired GB1330853A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US87801569A 1969-11-19 1969-11-19

Publications (1)

Publication Number Publication Date
GB1330853A true GB1330853A (en) 1973-09-19

Family

ID=25371195

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4950870A Expired GB1330853A (en) 1969-11-19 1970-10-19 Apparatus for controlling the acceleration of a gas turbine

Country Status (5)

Country Link
CH (1) CH513327A (en)
DE (1) DE2053286A1 (en)
FR (1) FR2069662A5 (en)
GB (1) GB1330853A (en)
NL (1) NL7016355A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2456213A1 (en) * 1979-05-07 1980-12-05 United Technologies Corp STARTING CONTROL FOR A GAS TURBINE ENGINE
EP0399692A1 (en) * 1989-05-23 1990-11-28 ROLLS-ROYCE plc Gas turbine engine fuel control system with enhanced relight capability
WO2003060303A1 (en) * 2002-01-09 2003-07-24 Ebara Corporation A gas turbine apparatus and a starting method thereof

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1122646B (en) * 1979-07-27 1986-04-23 Hydroart Spa IMPROVEMENT OF SPEED REGULATION SYSTEMS OF FIRST HYDRAULIC OR THERMAL ENGINES

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2456213A1 (en) * 1979-05-07 1980-12-05 United Technologies Corp STARTING CONTROL FOR A GAS TURBINE ENGINE
DK151487B (en) * 1979-05-07 1987-12-07 United Technologies Corp CONTROL FOR STARTING A GAS TURBINE
EP0399692A1 (en) * 1989-05-23 1990-11-28 ROLLS-ROYCE plc Gas turbine engine fuel control system with enhanced relight capability
US5129221A (en) * 1989-05-23 1992-07-14 Rolls-Royce Plc Gas turbine engine fuel control system with enhanced relight capability
WO2003060303A1 (en) * 2002-01-09 2003-07-24 Ebara Corporation A gas turbine apparatus and a starting method thereof
US7000405B2 (en) 2002-01-09 2006-02-21 Ebara Corporation Gas turbine apparatus and a starting method thereof

Also Published As

Publication number Publication date
CH513327A (en) 1971-09-30
DE2053286A1 (en) 1971-05-27
NL7016355A (en) 1971-05-24
FR2069662A5 (en) 1971-09-03

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees